THRUSH AIRCRAFT, INC – MODEL S2R-R1340
AIRCRAFT MAINTENANCE MANUAL
LANDING GEAR, WHEELS
AND BRAKES
GENERAL DESCRIPTION
Ref. Figures 6-1 & 6-2
Each main landing gear installation
consists of a landing gear assembly,
shock strut assembly and a wheel and
brake assembly. The landing gear
assembly is bolted to the fuselage frame
at two locations and to the shock strut
assembly at one location. The shock
strut assembly is in turn bolted to the
fuselage frame. Lubrication fittings are
provided for the pivot points and for the
shock strut assembly. Lubrication should
be applied sparingly and all parts wiped
clean to prevent collection of dirt (refer to
lubrication Chart, Section 2). All landing
gear hinge points should be carefully
inspected for wear and damage during
each landing gear check. Troubleshoot
the landing gear by using the charts at
the back this section, and always places
the aircraft on jacks prior to performing
maintenance procedures on the landing
gear system.
The tail gear is comprised of the trunnion
attach points on the fuselage, the tail
gear spring, the tail gear spring supports,
the housing and spindle, the centering
springs and unlock control cable, the
tailwheel yoke and axel, the wheel, the
tire & tube, and various assembly and
attaching hardware..
The tailwheel spring is attached at the
forward end to a trunnion which allows
limited fore and aft movement of the
spring. The spring is supported just
forward of the bend by clamping brackets
which support it and limit fore and aft
motion. The housing and spindle is
attached to the lower end of the tailwheel
spring, and the yoke is attached to the
housing.
Service of the tailwheel consists of
lubrication of the spindle and axel, plus
periodic repacking of the wheel bearings.
Attachment integrity should be inspected
daily visually and by rocking the aft
fuselage from side-to-side while
observing attachment points. Tire
inflation should be checked prior to every
flight.
The tailwheel is free castering when
unlocked, which is only when the control
stick if full forward. Otherwise it is locked
in the straight ahead position.
MAIN LANDING GEAR
MAIN LANDING GEAR ASSEMBLY
Ref. Figure 6-1
REMOVAL
A. Jack aircraft as outlined in Section 2.
B. Remove fuselage skins as required.
C. Disconnect flexible hydraulic brake
line at top of landing gear assembly.
D. Remove bottom bolt from shock strut
assembly.
E. Remove the bolts attaching landing
gear assembly to fuselage.
CLEANING, INSPECTION AND REPAIR
OF MAIN GEAR
A. Clean all parts with a suitable type
cleaning solvent.
B. Inspect all bolts, bearings and
bushings for excess wear, corrosion
and damage.
C. Check all welds for cracks.
D. Repair of the landing gear is limited
to reconditioning of parts, such as
replacing components, bearings and
bushings, smoothing out minor nicks
and scratches and repainting areas
where paint has chipped or peeled
6-2
Effective:
01/01/08
